Shevchenko S. Perfection of the rocket engine pneumatic starting system by stabilization of its actuating medium pressure and improvement of dynamic characteristics

The subject of this research is thermodynamic, gas-dynamic and vibromechanical processes of liquid-propellant rocket engine pneumatic starting system. The purpose of research is improvement of characteristics of the pneumatic starting system due to use of a pneumatically controlled pressure regulator and implementation of recommendations for adjusting parameters of this regulator. Research methods are experimental and theoretical methods based on the methods of thermodynamics, gas dynamics, vibromechanics, automatic control theory, mathematical physics and operational calculus. Theoretical and practical results are complex of analytic, computational and experimental research methods is developed that allows foreseeing and improving the pneumatic system characteristics, carrying out the gas-dynamic and thermodynamic calculations of its operating and life cycles, performing an analysis of dynamic stability and self-oscillation. The novelty is the following. Effects of inertance of gas in spherical tanks, dependence of internal energy on helium pressure, pressure penetration into a sealing gap of collar, compressibility of gas in a closed cavity at linearization, were taking into account in course of modeling. Gas pressure wave propagation velocity through the channel with corrugated wall was experimentally determined. The realization degree is application of the pneumatic system of startup in еру main liquid-propellant rocket engine RD861K of the launch vehicle "Cyclone-4". The branch of the research application is rocket and space industry.